An assembly for an aircraft propulsion system (20) includes a bladed rotor (24) and a thrust vectoring exhaust nozzle (100). The bladed rotor (24) is rotatable about an axis (28). The thrust vectoring exhaust nozzle (100) is configured to direct gas propelled by the bladed rotor (24) out of the aircraft propulsion system (20) along a first direction during a first mode and along a second direction during a second mode. The first direction is parallel with the axis (28) or angularly offset from the axis (28) by no more than five degrees. The second direction is angularly offset from the axis (28) by at least seventy-five degrees. The thrust vectoring exhaust nozzle (100) has a first exit area (109A) during the first mode and a second exit area (109B) during the second mode that is greater than the first exit area (109A).
THRUST VECTORING EXHAUST NOZZLE FOR AIRCRAFT PROPULSION SYSTEM
SCHUBVEKTORISIERUNGSABGASDÜSE FÜR EIN FLUGZEUGANTRIEBSSYSTEM
TUYÈRE D'ÉJECTION À ORIENTATION DE POUSSÉE POUR SYSTÈME DE PROPULSION D'AÉRONEF
2023-11-29
Patent
Electronic Resource
English
Thrust Vectoring Nozzle for Military Aircraft Engines
British Library Conference Proceedings | 2000
|Thrust Vectoring Nozzle for Modern Military Aircraft
NTIS | 2000
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